Driving means for aeroplane propellers



Patented Oct. 11, 1927.

UNITED, STATES PATENT OFF-ICE.

ANTON NOSAN, OF CLEVELAND, OHIO.

DRIVING MEANS FOR AEROIPLANE rnornrnnns.

Application filed August 18, 1926. Serial No. 129,981.

operating lever. The embodiment shown herein efiects the simultaneousoperation of both propellers by means of gears between the engine shaftand the propeller shafts, the propellers being located side by side atthe end of the aeroplane, but staggered transversely and with the platesset at right angles to each other so that each plate acts on a differentportion of the air, altho the propeller shafts may be set so close toeach other that the pairs of blades overlap.

The invention is illustrated in the accompanying drawings, in which Fig.l is a fragmentary view of the aeroplane with the improved propellerarrangement. Fig. 2 is a front view thereof.

The engine is indicated at. 5 mounted in the present showing in nose 6of the fuselage 7 and the engine crank shaft 10 has near its end adriving gear 9 which meshes at oppo site sides with driven gears 11 on apair of propeller hubs 12 having blades 13 mounted thereon.

These blades may be pivoted to the hub and turned or reversed by meansdescribed in my said pending application, said means including springcollars 14 having grooves 15 engaged by fingers 16 of sleeve'17 slidablymounted on the propeller supporting arms 18 extending along theoppositesides of the nose 6 of the fuselage. The hubs 12 are journalled in across bracket 19 mounted on the front of the-fuselage, which holds thepropellers in position. The sleeves 17 are connected by rods 20 to racks21 which mesh with pinions 22 carried by transverse shaft 23 which maybe turned by a lever 24 in the control compartment, these rods and shaftbeing carried in suitable supports on the fuselage. The itch .or angleof both propellers may be adjusted by the operation of lever 24 whichshifts the rods 20 backwardly or forwardly and by the means describedturns the propeller blades to different angles. The details of thedevices in hubs 12 may be such as those shown in my said pendmgapplication or any other suitable devices for adusting the pitch of theblades.

It will be noted that one propeller is set sufficiently in advance ofthe other to enablethe blades of the different propellers to, pass eachother, as particularly shown in Fig. 1.

Also, the ,blades are set at right angle so that they act on differentportions of air or other medium. This staggered arrangement permits theuse of two propellers in a close compass and with the full effect ofeach propeller. It is obvious that by means of gears 9 and 11 bothpropellersare driven from the single crank shaftand a very effectiveoperation is produced. Altho the propellers are illustrated at the frontof the machine, obviously they may be changed to opposite ends. Thesupports and gearing for the two propellers are simple and easilyaccessible, and the arrangement permits the convenient mounting of bladeshifting mechanism on a stationary support at each side of the fuselage,and the adjustment is simultaneous and equal for bot-h propellers, sothat no distortion or change of direction follows from such adjustment.

Various changes may be made within the scope of the invention as definedin the following claim.

I claim The combination with an aeroplane. fuselage, of a cross bracketmounted on one end thereof, twin propellers with adjustable blades,having hubs mounted in bearings at opposite ends of said bracket onopposite sides of the center line of the fuselage, a single enginemounted in the fuselage, and having a shaft projecting therefrom betweensaid hubs, gearing between the shaft' and the propeller hubs, at theouter side of said racket, and control rods for adjustin the blades,extending into the hubs at the inner side of said bracket.

In.testimony whereof, I do affix my signature.

ANTON NOSAN.

